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Shock Waves pp 413-418 | Cite as

Nozzle flow calibration of high enthalpy shock tunnel HIEST

  • T. Komuro
  • H. Tanno
  • K. Sato
  • S. Ueda
  • K. Itoh
Conference paper

Abstract

In the free piston shock tunnel HIEST, the free stream was disturbed due to nozzle throat melting. To maintain a uniform free stream, a new nozzle throat was designed by short- ening the subsonic part length. The new nozzle throat was examined in HIEST tests and no melting marks were observed. A uniform free stream was also maintained.

Keywords

Shock Tube Free Stream Nozzle Throat Shock Tunnel Nozzle Axis 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. 1.
    K. Itoh, S. Ueda, H. Tanno, T. Komuro, K. Sato: Hypersonic aerothermodynamics and scramjet research using high enthalpy shock tunnel. Shock Waves 12, 93 (2002)ADSCrossRefGoogle Scholar
  2. 2.
    K. Itoh, M. Takahashi, T. Komuro, K. Sato, H. Tanno, S. Ueda: ‘Effect of Throat Melting on Nozzle Flow Characteristics in High Enthalpy Shock Tunnel’. In: Proceedings of the 22nd International Symposium on Shock waves, 1999 Google Scholar
  3. 3.
    S. Nakano, K. Segawa, H. Itami, T. Takakusaghi, N. Matsuda, S. Yamaguchi: ‘A Study on Thermal Protection of a High Enthalpy Shock Tunnel’. In: Proceedings of the 20th International Symposium on Shock waves, 1997 Google Scholar

Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • T. Komuro
    • 1
  • H. Tanno
    • 1
  • K. Sato
    • 1
  • S. Ueda
    • 1
  • K. Itoh
    • 1
  1. 1.Japan Aerospace Exploration AgencyKakuda, MiyagiJapan

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